Abstract: A system is described that is configured to determine a plurality of air data parameters for an air vehicle. The system includes a mass air flow sensor, a pressure sensor, and a controller. The mass air flow sensor is mounted to sense an air flow caused by movement of the air vehicle. The pressure sensor is mounted to sense a static pressure at the air vehicle. The controller is configured to receive signals from the mass air flow sensor and the pressure sensor and determine an air velocity and a static pressure using the received signals.

Abstract: A method for controlling a detonation altitude of a radar equipped munition is described. The method includes calculating a velocity of the munition while the munition is at an altitude greater than the desired detonation altitude, determining when the munition is at a reference altitude, and calculating a time representing when the vehicle will reach the desired detonation altitude based on the calculated velocity and determined reference altitude. The method also includes generating a fusing signal to detonate the munition after the calculated time has passed.

Abstract: A method for characterizing pressure sensors to improve accuracy in an air data system is described where the sensors include at least one static pressure sensor and at least one total pressure sensor. The method includes characterizing the static pressure sensor and the total pressure sensor to determine a static pressure sensor error, Pse, and a total pressure sensor error, Pte, and performing a second ratiometric characterization to reference the total pressure sensor error, Pte, to the static pressure sensor error, Pse.

Abstract: A radar sensor is described that includes a radar transmitter, a radar receiver configured to receive reflected returns of signals output by the radar transmitter, and a signal processing unit configured to process signals received by the radar receiver. The signal processing unit includes a comparator, a first filter comprising an output coupled to a reference input of the comparator, and a second filter comprising an output coupled to a signal input of the comparator. The first and second filters are configured to receive a common input related to the reflected returns. The first filter is configured to have a time constant such that a rise time of the first filter output is faster than a rise time of the second filter output.

Abstract: An air data system and method for a rotary aircraft is described. The air data system includes a plurality of flush ports connected via tubing to a plurality of air flow sensors that can measure air flow speeds as low as approximately 0.02 knots. The flush ports are arranged around a main rotor shaft and below a rotor hub of the rotary aircraft to help reduce the impact of rotor downwash. The flush ports and tubing permit air to flow into the air flow sensors, which allows the plurality of air flow sensors to measure speed and direction of cross-wind components of air flow surrounding the rotary aircraft.

Abstract: A sensing device is described that is configured to be launched from an air vehicle for deployment on the ground. The sensing device includes at least one sensor, an inertial measurement unit (IMU), at least one flight control surface, a flight control unit configured to control a position of the flight control surfaces, and a processing unit. The processing unit is coupled to the IMU and is configured to receive a desired trajectory from an external source and, upon launch of the sensing device, is further configured to determine an error between the desired trajectory and a current position as determined by the IMU. The processing unit is also configured to cause the flight control unit to adjust a position of the flight control surfaces to minimize the error.

Abstract: A system for determining airspeed of an air vehicle is described which includes and airflow sensor and a processor. The airflow sensor is located within an airflow path extending substantially through the air vehicle, and the processor is configured to receive a signal relating to an airflow rate from the airflow sensor and output an airspeed based on the received signal.

Abstract: A security system is described which includes a base station, at least one calibration unit and at least one sensor module having at least one sensor therein. The calibration unit is configured to provide signals to the at least one sensor module. The signals contain data configured to at least partially enable each sensor module to determine its location within a coordinate system. Each sensor module is further configured to transmit module location data, module orientation data, and sensor status from each sensor to the base station.

Abstract: An air data sensor for an aircraft has a flush mounted plate at the outside surface of the aircraft and a housing for the sensor within the aircraft below the plate. A plurality of holes in the plate provide air flow to a pressure sensor in the housing. To prevent water from reaching the sensor, a trap chamber is provided below the holes. Various contorted air flow paths are disclosed. The tube to the pressure sensor may be heated.

Abstract: An air data sensor for an aircraft has a flush mounted plate at the outside surface of the aircraft and a housing for the sensor within the aircraft below the plate. A plurality of holes in the plate provide air flow to a pressure sensor in the housing. To prevent water from reaching the sensor, a trap chamber is provided below the holes. Various contorted air flow paths are disclosed. The tube to the pressure sensor may be heated.